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Aerothermodynamics of a hypersonic projectile with a double-disk aerospike

机译：具有双盘气钉的高超声速弹丸的空气热力学

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摘要

The use of aerospikes at the nose of a hypersonic vehicle can substantially reduce its drag; however, the associated heat flux at the reattachment point is very high for turbulent flows. In this paper, the aerothermodynamics of a generic projectile model represented by a hemisphere- cylinder, fitted axisymmetrically with an aerospike at the nose is investigated numerically with a commercially available Navier Stokes Solver. The base model is a hemisphere-cylinder with a diameter of 40mm and an overall length of 70mm. An aerospike protrudes axisymmetrically at the nose of the base model and has a hemispherical cap from which another aerospike protrudes which again has a hemispherical cap, thus forming a double-disk aerospike. Compressible, axisymmetric Navier-Stokes Equations are solved for turbulent hypersonic flow of thermally perfect air with free stream conditions of Mach No 6-2 at standard sea level atmospheric conditions. The results for the model with double-disk aerospikes are compared with those of hemisphere-cylinder without aerospike. The results suggest that the use of double-disk aerospike can favourably reduce the turbulent reattachment heat flux along with suitable drag reduction of the main body.
机译：在超音速飞行器的机头处使用气钉可以大大减少其阻力。但是，对于湍流，在重新连接点的相关热通量非常高。在本文中，用市售的Navier Stokes Solver数值研究了以半球圆柱体为代表的通用射弹模型的空气热力学，该圆柱体在轴对称处安装有鼻翼。基本模型是直径为40mm，总长度为70mm的半球形圆柱体。气钉在基本模型的鼻子处呈轴对称突出，并具有一个半球形的帽，另一个气钉从该半球形帽伸出，该气垫又具有一个半球形的帽，从而形成了双盘气钉。在标准海平面大气条件下，可压缩的轴对称Navier-Stokes方程求解了热完美空气的湍流高超音速流，自由流条件为6-2马赫。将具有双盘气雾的模型的结果与没有气雾的半球圆柱的结果进行比较。结果表明，使用双盘气雾化器可以很好地减少湍流重新附着的热通量，并适当减小主体的阻力。

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  • 来源
    《The Aeronautical Journal》 |2013年第1195期|913-928|共16页
  • 作者

    R. Yadav; U. Guven;

  • 作者单位

    University of Petroleum and Energy Studies Dehradun India;

    University of Petroleum and Energy Studies Dehradun India;

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  • 正文语种 eng
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